US20140322017A1 - Rotary mechanical system with contactless actuation - Google Patents

Rotary mechanical system with contactless actuation Download PDF

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Publication number
US20140322017A1
US20140322017A1 US14/357,623 US201214357623A US2014322017A1 US 20140322017 A1 US20140322017 A1 US 20140322017A1 US 201214357623 A US201214357623 A US 201214357623A US 2014322017 A1 US2014322017 A1 US 2014322017A1
Authority
US
United States
Prior art keywords
shaft
relation
mechanical system
movable member
drive means
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US14/357,623
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English (en)
Inventor
Cedric Duval
Eric DE WERGIFOSSE
Vincent Hidelot
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Electrical and Power SAS
Original Assignee
Hispano Suiza SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hispano Suiza SA filed Critical Hispano Suiza SA
Assigned to HISPANO SUIZA reassignment HISPANO SUIZA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DE WERGIFOSSE, ERIC, HIDELOT, Vincent, DUVAL, CEDRIC
Publication of US20140322017A1 publication Critical patent/US20140322017A1/en
Assigned to LABINAL POWER SYSTEMS reassignment LABINAL POWER SYSTEMS ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HISPANO SUIZA
Assigned to LABINAL POWER SYSTEMS reassignment LABINAL POWER SYSTEMS CORRECTIVE ASSIGNMENT TO CORRECT THE INCORRECT PATENT NO. 8487560 PREVIOUSLY RECORDED ON REEL 035149 FRAME 0874. ASSIGNOR(S) HEREBY CONFIRMS THE THE ASSIGNMENT. Assignors: HISPANO SUIZA
Assigned to SAFRAN ELECTRICAL & POWER reassignment SAFRAN ELECTRICAL & POWER CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: LABINAL POWER SYSTEMS
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/44—Blade pitch-changing mechanisms electric
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F04D29/36—Blade mountings adjustable
    • F04D29/362—Blade mountings adjustable during rotation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F05D2270/023—Purpose of the control system to control rotational speed (n) of different spools or shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/62—Electrical actuators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a rotary electromechanical system comprising a member mounted on a movable shaft, which is suitable for being moved in relation the movable shaft.
  • the electromechanical system comprises a frictionless drive device wherein one component is movable in relation to the movable shaft, for which the service life of the drive device is enhanced by reducing friction between moving parts.
  • the blades are borne by a shaft rotatably mounted about the primary axis thereof.
  • Each blade is further movably mounted in relation to the shaft about a radial axis in relation to the main shaft axis, to modify the blade pitch.
  • the blades are rotated by means of a drive system which is connected to the blades and wherein one part is mounted on the structural element of the turbine engine.
  • the means for driving the blades consist of rotary seal hydraulic systems or rotary contact electrical of electronic systems.
  • Such embodiments comprise numerous movable elements which are in contact with each other. This results in component wear and significant heat production.
  • the mechanical system also comprises cooling and lubrication means for limiting the heating and wear of these components. Also, it is sometimes necessary to perform regular maintenance operations of the mechanical system.
  • the aim of the invention is that of providing a mechanical system for which the means for moving the blades in relation to the shaft are embodied so as to limit friction between the movable elements.
  • the invention relates to a mechanical system comprising:
  • the air gap between the two portions of the actuator make it possible to eliminate any contact between the elements connected to the structural element and the elements which are movable in relation to the structural element, thus reducing friction.
  • the drive means consist of a radial field air gap electromechanical actuator.
  • the drive means consist of an axial field air gap electromechanical actuator.
  • the second portion of the drive means is rotatably mounted coaxially with the shaft and is connected to the shaft by means for guiding in rotation about the primary axis of the shaft.
  • the mechanical system comprises means for converting the rotary motion of the second portion in relation to the shaft into a movement of the movable member in relation to the shaft which comprise a motion input member connected to the second portion, said motion input member being selectively rotatable in relation to the shaft during the movement of the movable member.
  • the mechanical system comprises means for controlling the drive means to control the rotational speed of the second portion of the drive means in relation to the first portion, according to the rotational speed of the shaft.
  • control means are embodied so as to cause rotation of the motion input member about the shaft to move the movable member in relation to the shaft.
  • the movable member is rotatably mounted in relation to the shaft about a secondary axis (B) having a radial orientation in relation to the primary axis, said secondary axis (B) being fixed to the shaft for rotation therewith about the primary axis.
  • the invention also relates to an aircraft turbine engine characterised in that it comprises a mechanical system according to any of the above claims, wherein the movable member consists of a variable orientation blade.
  • the turbine engine comprises a plurality of blades distributed about the primary axis of the shaft.
  • FIG. 1 is a schematic representation of a mechanical system according to the invention
  • FIG. 2 is a similar view to that in FIG. 1 , showing a second embodiment of the means for converting motion;
  • FIG. 3 is a detailed schematic representation of a mechanical system according to the invention for which the drive means consist of a magnet asynchronous or asynchronous motor;
  • FIG. 4 is a similar view to that in FIG. 3 , wherein the drive means consist of a field coil synchronous motor;
  • FIG. 5 is a similar view to that in FIG. 3 , wherein the drive means consist of an axial air gap synchronous motor.
  • the figures represent a mechanical system 10 such as a turbine engine rotor comprising a rotatable shaft 12 about the primary axis A thereof, in relation to a structural element 14 of the turbine engine.
  • This structural element may in turn be fixed in the turbine engine, or it may be movable in the turbine engine.
  • the structural element 14 will be considered to be fixed in relation to the shaft 12 .
  • the shaft bears a plurality of blades 16 which are distributed evenly about the shaft 12 in relation to the primary axis A and which are fixed to the shaft 12 for rotation therewith in relation to the structural element 14 , about the primary axis A.
  • the mechanical system 10 comprises means for setting the pitch of the blades 16 in order to adapt the system to the operating conditions of the turbine engine.
  • each blade 16 is movably mounted in relation to the shaft 12 about a secondary axis B having a radial main orientation in relation to the primary axis A.
  • Each secondary axis B is a primary axis of the associated blade 16 , it is thus fixed to the shaft 12 for rotation therewith about the primary axis A.
  • the means for setting the pitch of the blades 16 comprise drive means 18 for rotating each blade 16 about the associated secondary axis B.
  • the drive means essentially comprise a first fixed portion 20 which is attached to the structural element 14 and a second movable portion 22 which is connected to each blade 16 .
  • the second portion is rotatably mounted in relation to the structural element 14 about the primary axis A.
  • first portion 20 and the second portion 22 are coaxial to the shaft 12 and consist of two rotating elements superposed radially on the shaft 12 .
  • the drive means 18 consist of an air gap electromechanical actuator. This means that a gap is present between the fixed portion 20 and the movable portion 22 .
  • the movable portion 22 is rotated in relation to the fixed portion 20 by means of electromagnetic forces requiring no contact between the two portions 20 , 22 .
  • the drive means 18 consist of a permanent magnet synchronous motor.
  • the movable portion 22 bears one or a plurality of permanent magnets (not shown) and the fixed portion 20 comprises means for producing an electromagnetic field inducing the rotation of the movable portion bearing the permanent magnet(s).
  • the drive means 18 consist of a field coil synchronous motor.
  • the movable portion 22 bears one or a plurality of windings which are supplied with electrical current so as to act as one or a plurality of electromagnets.
  • the movable portion 22 is powered by means of a current induction system 24 which is also of the contactless type.
  • the drive means 18 consist of an asynchronous motor.
  • the shaft 12 and the movable portion 22 both rotate about the primary axis A.
  • the mechanical system 10 is embodied such that the second portion 22 is suitable for rotating at a different speed to the rotational speed of the shaft 12 to enable the movement of the blades 16 .
  • the second portion 22 is guided in rotation about the primary shaft A by means 26 for linking the second portion 22 with the shaft 12 which are means for guiding the second portion 22 in rotation in relation to the shaft 12 about the primary axis A.
  • the second portion 22 of the drive means 18 is further connected to the blades 16 via motion conversion means 28 .
  • the motion conversion means 28 are mounted on the shaft 12 such that they are fixed to the shaft 12 for rotation therewith about the primary axis A.
  • the motion conversion means 28 comprise a motion input member 36 which is connected to the second portion 22 of the drive means 18 .
  • the motion conversion member 36 is suitable for rotating selectively about the shaft 12 according to the rotational speed of the second portion 22 of the drive means 18 about the primary axis A.
  • the motion conversion means 28 are embodied such that when the motion input member 36 rotates in relation to the shaft 12 , each blade 16 rotates about the associated secondary axis B.
  • the motion conversion means 28 are of the type comprising a bevel gear coupling 32 .
  • the motion conversion means 28 are of the type comprising a crankshaft system 34 .
  • the motion input member 36 is connected to the second portion 22 of the drive means 18 via a gear system 30 for modifying the rotational speed of the motion input member 36 about the primary axis A in relation to the rotational speed of the second portion 22 about the primary axis A.
  • the gear ratio of this gear system 30 is determined so as to reduce or increase the rotational speed of the second portion 22 , according to the type of actuator forming the drive means 18 and according to the rotational speed ranges of the shaft 12 .
  • the second portion 22 of the drive means 18 is connected directly to the motion input member 36 .
  • the drive means 18 also comprise regulation means (not shown) which are designed to regulate the rotational speed of the second portion 22 in relation to the structural element 14 according to the rotational speed of the shaft 12 in relation to the structural element 14 and according to the gear ratio of the gear system 30 .
  • the regulation means are embodied so as to selectively induce rotation of the motion input member in relation to the shaft 12 , when the orientation of the blades 16 needs to be modified.
  • the motion input member 36 should remain immobile in relation to the shaft 12 , i.e. it rotates at the same speed as the shaft 12 in relation to the structural element 14 .
  • the rotational speed of the second portion 22 in relation to the structural element 14 is defined so that the rotational speed of the motion input member 36 in relation to the structural element 14 is equal to the rotational speed of the shaft 12 in relation to the structural element 14 .
  • the regulation means modify the rotational speed of the second portion 22 in relation to the structural element 14 for a certain time so that the motion input member 36 rotates in relation to the shaft 12 by a predefined angle corresponding to the modification of angular position of each blade 16 .
  • the modification of the rotational speed of the second portion 22 in relation to the structural element 14 may consist of an increase, decrease or inversion of the rotational speed of the second portion 22 .
  • the regulation means modify the rotational speed of the second portion 22 in relation to the structural element 14 so that the motion input member 36 rotates at the same speed as the shaft 12 in relation to the structural element 14 and thus so that the motion input member 36 is immobile in relation to the shaft 12 .
  • the power supply frequency at the fixed portion 20 should offset the rotational speed of the shaft 12 in relation to the primary axis A.
  • the reference “F 12 ” is thus defined as being the differential rotation frequency of the shaft 12 in relation to the first portion 20 (for example for a rotational speed of the shaft 12 in relation to the primary axis A of 1200 rpm, this corresponds to a frequency F 12 of 20 Hz).
  • the reference “p” is also defined as being the number of pair of poles of the magnet synchronous motor.
  • the power supply is defined by the formula p*(F 12 +F 22 +Fr) where Fr is the rotor current frequency in the second portion 22 .
  • rotational speed of the second portion 22 may be modified continuously, to prevent any jerking.
  • the drive means 18 are of the radial field air gap type, i.e. the fixed portion 20 and the movable portion 22 are coaxial and are radially offset in relation to each other.
  • the invention is not limited to this embodiment and that the drive means 18 may be of another type, such as for example represented in FIG. 5 wherein the drive means are of the axial field air gap type.
  • the fixed portion 20 and the movable portion 22 are axially offset in relation to each other.
  • the drive means 18 are of the type combining a radial field air gap and an axial field air gap.
  • the invention has been described in associated with turbine engine blades 16 which are rotatable about the secondary axis B. It will be understood that the invention is not limited to this embodiment and that the invention may be associated with any element movably mounted along the secondary axis B in translation along the second axis B or according to motion combining translation and rotation in relation to the secondary axis B.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
  • Dynamo-Electric Clutches, Dynamo-Electric Brakes (AREA)
  • Transmission Devices (AREA)
US14/357,623 2011-11-24 2012-11-23 Rotary mechanical system with contactless actuation Abandoned US20140322017A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1160764 2011-11-24
FR1160764A FR2983235B1 (fr) 2011-11-24 2011-11-24 Systeme mecanique tournant a actionnement sans contact
PCT/FR2012/052710 WO2013076431A1 (fr) 2011-11-24 2012-11-23 Système mécanique tournant a actionnement sans contact description

Publications (1)

Publication Number Publication Date
US20140322017A1 true US20140322017A1 (en) 2014-10-30

Family

ID=47436057

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/357,623 Abandoned US20140322017A1 (en) 2011-11-24 2012-11-23 Rotary mechanical system with contactless actuation

Country Status (9)

Country Link
US (1) US20140322017A1 (fr)
EP (1) EP2782827A1 (fr)
JP (1) JP2015500933A (fr)
CN (1) CN103958346B (fr)
BR (1) BR112014012388B1 (fr)
CA (1) CA2854991A1 (fr)
FR (1) FR2983235B1 (fr)
RU (1) RU2642683C2 (fr)
WO (1) WO2013076431A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT523262A4 (de) * 2020-01-29 2021-07-15 Manuel Schleiffelder Mag Vorrichtung zur Verstellung der Neigung von Rotorblättern eines Rotors
EP4369576A1 (fr) * 2022-11-10 2024-05-15 YourSky Management Machine à induction avec mécanisme d'angle de pale variable
US20240337195A1 (en) * 2021-08-04 2024-10-10 Safran Aircraft Engines Fan module having variable-pitch blades

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3060523B1 (fr) * 2016-12-21 2019-05-17 Safran Aircraft Engines Systeme d'actionnement electromecanique de pas pour une helice de turbomachine
FR3060525B1 (fr) * 2016-12-21 2022-03-11 Safran Aircraft Engines Systeme d'actionnement electromecanique de pas pour une helice de turbomachine
FR3060526B1 (fr) * 2016-12-21 2019-05-10 Safran Aircraft Engines Systeme d'actionnement electromecanique de pas pour une helice de turbomachine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2370135A (en) * 1941-09-25 1945-02-27 Engineering & Res Corp Variable pitch propeller
US5281095A (en) * 1990-12-20 1994-01-25 Honda Giken Kogyo Kabushiki Kaisha Variable-pitch mechanism for a propeller
US5281094A (en) * 1991-05-13 1994-01-25 Alliedsignal Inc Electromechanical apparatus for varying blade of variable-pitch fan blades
US5282719A (en) * 1991-05-13 1994-02-01 Alliedsignal Inc. Quad mode fan pitch actuation system for a gas turbine engine
US5595474A (en) * 1993-11-10 1997-01-21 Hispano-Suiza Pitch variation control device for the blades of a turbomachine rotor and method of operating the device
US20060284509A1 (en) * 2005-06-16 2006-12-21 Lg Electronics Inc. Induction motor
US20080174194A1 (en) * 2006-12-07 2008-07-24 General Electric Company Double-Sided Starter/Generator for Aircrafts

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB545195A (en) * 1941-11-07 1942-05-14 Constant Speed Airscrews Ltd Improvements in aircraft
US4948337A (en) * 1989-05-01 1990-08-14 United Technologies Corporation Aircraft engine propulsor blade pitch sensing
US5451141A (en) * 1993-12-23 1995-09-19 United Technologies Corporation Propeller pitch change machanism with inductive brake and motor
GB2313415B (en) * 1993-12-23 1998-05-20 United Technologies Corp Propeller or fan pitch change mechanism with inductive brake and motor
US7118336B2 (en) * 2003-12-19 2006-10-10 Pratt & Whitney Canada Corp. Pressurized oil supply for propeller engine system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2370135A (en) * 1941-09-25 1945-02-27 Engineering & Res Corp Variable pitch propeller
US5281095A (en) * 1990-12-20 1994-01-25 Honda Giken Kogyo Kabushiki Kaisha Variable-pitch mechanism for a propeller
US5281094A (en) * 1991-05-13 1994-01-25 Alliedsignal Inc Electromechanical apparatus for varying blade of variable-pitch fan blades
US5282719A (en) * 1991-05-13 1994-02-01 Alliedsignal Inc. Quad mode fan pitch actuation system for a gas turbine engine
US5595474A (en) * 1993-11-10 1997-01-21 Hispano-Suiza Pitch variation control device for the blades of a turbomachine rotor and method of operating the device
US20060284509A1 (en) * 2005-06-16 2006-12-21 Lg Electronics Inc. Induction motor
US20080174194A1 (en) * 2006-12-07 2008-07-24 General Electric Company Double-Sided Starter/Generator for Aircrafts

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT523262A4 (de) * 2020-01-29 2021-07-15 Manuel Schleiffelder Mag Vorrichtung zur Verstellung der Neigung von Rotorblättern eines Rotors
AT523262B1 (de) * 2020-01-29 2021-07-15 Manuel Schleiffelder Mag Vorrichtung zur Verstellung der Neigung von Rotorblättern eines Rotors
US20240337195A1 (en) * 2021-08-04 2024-10-10 Safran Aircraft Engines Fan module having variable-pitch blades
EP4369576A1 (fr) * 2022-11-10 2024-05-15 YourSky Management Machine à induction avec mécanisme d'angle de pale variable
WO2024099601A1 (fr) * 2022-11-10 2024-05-16 Yoursky Management Machine à induction dotée d'un mécanisme à angle de pale variable

Also Published As

Publication number Publication date
FR2983235A1 (fr) 2013-05-31
FR2983235B1 (fr) 2018-04-13
EP2782827A1 (fr) 2014-10-01
CN103958346A (zh) 2014-07-30
JP2015500933A (ja) 2015-01-08
RU2642683C2 (ru) 2018-01-25
CA2854991A1 (fr) 2013-05-30
BR112014012388A2 (pt) 2017-05-30
BR112014012388B1 (pt) 2021-05-25
RU2014125431A (ru) 2015-12-27
CN103958346B (zh) 2016-08-17
WO2013076431A1 (fr) 2013-05-30

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